Apparatus and method for gyroscopic propulsion

ABSTRACT

The present invention is a combination of three interconnected gyroscopic ring-like rotating masses, with each of the three ring-like masses being configured to rotate in various planes, depending on the desired orientation. Regardless of the orientation of the three rings, each of the three interconnected rotating masses will share substantially the same center of gravity and generate a separate yet interactive kinetic energy and angular momentum in each of the three planes, thereby providing resistance to rotational forces from external sources. This is known as &#34;equal force presence.&#34; Additionally, a series of pedestal supports for supporting the three ring-like masses is disclosed.

RELATED APPLICATIONS

This application is a divisional of U.S. patent application Ser. No.10/770,795, filed on Feb. 3, 2004, which patent application is presentlypending and which application is a continuation-in-part of U.S. patentapplication Ser. No. 10/087,430, filed on Mar. 1, 2002, now issued asU.S. Pat. No. 6,705,174, all of which are incorporated herein byreference.

BACKGROUND OF THE INVENTION

1. Technical Field

The present invention relates generally to rotational forces and morespecifically relates to creating a linear movement from a system ofrotational forces.

2. Background Art

Propulsion of an object not in contact with a relatively fixed body, forexample the ground or a planet surface, is generally obtained only bymovement of air or other gases in a direction substantially opposite tothe movement of the object under the effect of the propulsion systems.In the absence of a suitable atmosphere, for example in space,propulsion is generally obtained by rocket systems or by other similarsystems which involve the projection of particles at high velocity fromthe object, in the opposite direction of the object's intended travel.Such systems, by their very nature and design, require the consumptionof significant quantities of fuel since the fuel or the byproducts ofthe consumption or expulsion of the fuel forms the particles to beprojected.

Attempts have been made for many years to develop a propulsion system,which generates linear movement from a rotational drive. Examples ofthis type of arrangement are shown in a book entitled “The Death ofRocketry” published in 1980 by Joel Dickenson and Robert Cook.

However none of these previous arrangements has in any way provedsatisfactory and if any propulsive effect has been obtained this hasbeen limited to simple models. One of the problems with the previousattempts is the limited understanding of the true nature of the laws ofmotion and the nature of the physical universe. The laws of motion, ascurrently defined and used in the scientific community, are onlyaccurate to a limited degree of precision. Many conditions andqualifications are required to apply them to the physical world, as itactually exists. This is far truer for the quantification of angularmotion than it is for more linear motion. The laws of motion postulatedby Newton are built upon his first law of inertia and are generallyregarded as the foundation of Einstein's theory of relativity.

In the cosmos, everything is moving and there is no such thing that isperfectly static and motionless. The very first law of physics involvesconcepts that are only proper in a given frame of reference. Consider abody “at rest.” The idea of “at rest” implies a lack of motion. However,the object is only “at rest” with respect to the relative motion of theobject's immediate environment. Matter “at rest” is actually moving inpatterns of motion that create the appearance of static motionlessness,yet the accumulated energies within the matter, in addition to therelative motion of the composite cosmic environment, is well known andprovides sufficient evidence that everything is in a state of constantmotion. Inertia, as it is generally referred to in relation to the lawsof physics, represents relatively balanced force relationships creatingrelatively constant and stable motion patterns.

The basic formulas typically used to describe various angular forces aresufficient to explain only the most basic concepts relative to thebehavior of spinning masses. They are the accepted formulas of Newtonianphysics for linear motion applied to rotation with the linear componentsexchanged for angular ones. Rotational inertia is generally defined withthe appropriate embellishments necessary to include the shape of themass about the axis of rotation as an additional factor in the magnitudeof the inertia.

Newton's first law of motion dealing with inertia and the inertialreference frames used in the calculation of linear forces do not, in thestrictest sense, apply to rotational force associations. Inertialreference frames are usually linear by qualification and rotating framesof reference are never inertial. This fact is not a significant factorto include in the calculations of most linear forces. In most cases ofordinary motion, the angular components in the inertial reference frameare negligible. For example, air resistance is frequently a negligiblefactor in certain cases and, in those cases, can therefore be ignored.Or as the limitations of the linear velocity of things is ignored unlesssufficiently close to the recognized maximum. Similarly, the non-linearcomponents of most inertial reference frames ignored, and can be, formost ordinary kinds of motion. The additional factor of shape foreverqualifies the angular motion aspects of particle associations withrespect to the force of that association. This is the most meaningfuland valuable factor separating the behavior of angular force from linearforce.

Motion on a scale large enough with respect to the earth and the cosmicenvironment to be substantially non-linear can never be ignored. Andthis is not the case with most kinds of ordinary motion. In thefundamentals of physics, this fact is considered significant only forlarge-scale motions such as wind and ocean currents, yet “strictlyspeaking” the earth is not an inertial frame of reference because of itsrotation. The earth's non-linear character is observed in the case ofthe Foucault pendulum, the Coriolis Effect, and also in the case of afalling object which does not fall “straight” down but veers a little,with the amount of deviation from its path dependant on the period oftime that elapses during the fall. All events are subject to this factto a greater or lesser extent.

The mathematical purpose of inertial reference frames is to isolate amotion event in order to identify force components. Acceleration willonly be observed in systems that have a net force in a given directionand are not balanced or zero. Since this is only valid for the linearcomponents of motion, it works well for all kinds of motion phenomenathat are primarily linear in nature; the associated angular componentbeing either idealized or considered negligible. Only the linear forceaspects of any of these measurements hold precisely true to the formulasof mathematics describing them. To the degree that angular components ofmotion are associated with the reference frame used for measuring andcalculating force relationships, and to the extent which these angularcomponents are not included in the formulas for calculation, is to thedegree these formulas are in error. The fact that angular referenceframes cannot and do not represent inertial reference frames indicatesthat the effect of angular force is not so easily isolated in order toidentify component effects.

Mathematical analysis of rotational forces reveals that the formulasdescribing rotational motion are also limited in additional respects.Motions that include anything more than ninety degrees of rotationcannot be used as true vectors. The fundamental technique of vectors,used to determine the composite result of the effect of multiple forces,will not work for rotational motion due to the inherent lack ofintegrity in the model. Individual angular displacements, unless theyare small, can't be treated as vectors, though magnitude and directionof rotational velocity at a particular point in time and space can begiven, which is necessary. But this alone is not sufficient, because therules of vector mathematics do not hold with regard to the order of theaddition of these forces.

If the displacement of an object is given by a series of rotationalmotions, the resulting angular position of the object is differentdepending on the order of the sequence of angular motions. Vectormathematics requires that addition be commutative (a+b+c=c+b+a). Tocalculate the motion of the precessional adjustments which multipledisturbing torques have on a spinning mass in a dynamic environmentrequires extremely complex mathematical calculations and is notaccounted for in the previous attempts to translate rotational energyinto linear movement.

The fact that these precessional adjustments can be affected by a strongmagnetic field, and that there are no mathematical formulas that includethis phenomenon as a factor of calculation, demonstrates that angularmomentum is not fully predictable by the current formulas of mathematicsand this is why there has been no true success in developing anapparatus which can efficiently and effectively use the angular momentumof a spinning mass to create a controlled linear movement.

The simple systems of motion that involve a magnitude of angularmomentum that is relatively large with respect to the mass of therotating body all exhibit nuances or nutation of precessional adjustmentnot described by the force components given by the accepted formulas ofphysics for angular motion. The Levitron is one excellent example, andthere are additional examples that reveal how the rotating systems ofmotion in the natural environment are significantly more complicatedthan is typically described by the formulas associated with thesepatterns.

When these motions are recreated, using the accepted formulas for thesepatterns, the motion is not at all like the naturally observed versionsand is sterile and fixed, lacking the nuances and nutation that exist inthe cosmic environment. The nuances and nutation of spinning motionsobserved in nature are typically complex composite angular effects ofthe local cosmic environment, down to and including the immediateangular motions of observation. This is why a typical gyroscope tends todispose its axis parallel to the earth's in an effort to achieve overalldynamic equilibrium within the total environment. All angular motion isaffected by all other angular motions, at least to some degree and aclose examination reveals that everything moving is affected to acertain extent. However, rotating systems of force generate a motionpattern that can be used to magnify this interactive effect and,therefore, reveal the influence of the cosmic environment on thesepatterns of revolving motion.

When the cosmic influences are analyzed, any and all of the motions ofanything and everything include some factor of angular displacement. Aperfectly straight line is only a concept with respect to a mathematicalidea. In reality, nothing moves in absolutely linear displacements, toone degree or another, there is typically an angular component to allmotions. Even the primarily linear trajectories associated withelectromagnetic radiation are slightly curved and this phenomenon can bereadily observed in the vast stretches of outer space. In many cases,the angular component of motion is negligible for all practical intentsand purposes, in other cases, it is the primary force of action, but inno case is it non-existent.

Gravity is the reason: the closer an object is to a strong gravitationalforce, the greater the amount of angular displacement in the surroundingmotions. Astrophysicists account for this influence on the light of faraway galaxies and describe the effect as a gravitational lens. Gravityexerts a torque on all matter within its grasp. This is a factor thatshould be included in relativity's equivalence principle to furtherqualify otherwise pure linear acceleration. The angular paths of movingbodies create the inevitability of a cosmic torque in the spatial frameof any gravitational mass. The Coriolis Effect is a composite result ofthe force of gravity in association with the rotating circular path ofany given rotating system. As it is ordinarily viewed, the effect onlarge-scale motions on the surface of any revolving sphere is withrespect to linear latitude until reaching a minimum at the poles. Acritical examination will show that the angular component of motion isthe same everywhere on the planet. Only the angle, with respect to thedirection of the force of gravity, changes from the equator to thepoles. At the equator, the radius, with respect to the axis of rotation,is greatest; this maximizes the effect on linear motions and is used toadvantage when launching rockets into orbit around a sphere.

This bending of motion associated with gravity is the fundamentalrequirement to achieve a universe that behaves as if having purelylinear forces on all but the largest scale of cosmic proportions. Allstraight lines of motion are ultimately elliptical curves. Accordingly,without an improved understanding of the forces associated with spinningmasses and the influence of the gravitational field that is associatedwith movement of objects in general, it will be impossible to createdevices that maximize the use of spinning masses and rotational energyto create linear motion. This means that any device which attempts toharness the kinetic energy and possible advantages based on theseprinciples will continue to be sub-optimal.

DISCLOSURE OF INVENTION

The present invention is a combination of three interconnectedgyroscopic ring-like rotating masses, with each of the three ring-likemasses being configured to rotate in various planes, depending on thedesired orientation. Regardless of the orientation of the three rings,each of the three interconnected rotating masses will sharesubstantially the same center of gravity and generate a separate yetinteractive kinetic energy and angular momentum in each of the threeplanes, thereby providing resistance to rotational forces from externalsources. This is known as “equal force presence.” Additionally, a seriesof pedestal supports for supporting the three ring-like masses isdisclosed.

BRIEF DESCRIPTION OF DRAWINGS

The preferred embodiments of the present invention will hereinafter bedescribed in conjunction with the appended drawings, wherein likedesignations denote like elements, and:

FIG. 1 is a perspective view of the three planes for initial rotation ofthe three gyroscopic rings of a gyroscopic propulsion apparatusaccording to a preferred embodiment of the present invention;

FIG. 2 is an exploded view of the three main components in a singlegyroscopic ring used in a gyroscopic propulsion apparatus in accordancewith a preferred embodiment of the present invention;

FIG. 3 is a plan view of the surface of the rotor for one of the threegyroscopic rings of a gyroscopic propulsion apparatus in accordance witha preferred embodiment of the present invention;

FIG. 4 is a plan view of the external housing for the rotor portion ofthe ring of FIG. 3;

FIG. 5 is a sectional view of a portion of the bearing assembly of therotor portion of the gyroscopic ring of FIG. 3;

FIG. 6 is a perspective view of a superstructure created from threegyroscopic rings in accordance with a preferred embodiment of thepresent invention;

FIG. 7 is a perspective view of a housing for the three gyroscopic ringsin accordance with a preferred embodiment of the present invention;

FIG. 8 is a block diagram of the control circuits for a gyroscopicpropulsion apparatus in accordance with a preferred embodiment of thepresent invention;

FIG. 9 is a perspective view of a vehicle incorporating a gyroscopicpropulsion apparatus in accordance with a preferred embodiment of thepresent invention;

FIG. 10 is a top view of a z-plane pedestal component in accordance witha preferred embodiment of the present invention;

FIG. 11 is a top view of a y-plane pedestal component in accordance witha preferred embodiment of the present invention;

FIG. 12 is a top view of a x-plane pedestal component in accordance witha preferred embodiment of the present invention;

FIG. 13 is an exploded view of a half pedestal in accordance with apreferred embodiment of the present invention;

FIG. 14 is an perspective view of an assembled half pedestal inaccordance with a preferred embodiment of the present invention;

FIG. 15 is an exploded view of a complete pedestal in accordance with apreferred embodiment of the present invention;

FIG. 16 is a perspective view of two pedestal halves in accordance witha preferred embodiment of the present invention;

FIG. 17 is a perspective view of an assembled pedestal in accordancewith a preferred embodiment of the present invention;

FIG. 18 is a perspective view of two pedestal halves with one pedestalhalf supporting the three gyroscopic rings in accordance with apreferred embodiment of the present invention;

FIG. 19 is a perspective view of an assembled pedestal containing thethree gyroscopic rings in accordance with a preferred embodiment of thepresent invention;

FIG. 20 is perspective view of an alternative housing in accordance witha preferred embodiment of the present invention;

FIG. 21 is a perspective view of the housing containing the assembledpedestal and the three gyroscopic rings in accordance with a preferredembodiment of the present invention;

FIG. 22 is a perspective view of the three gyroscopic rings fixed inposition relative to each other in accordance with an alternativepreferred embodiment of the present invention;

FIG. 23 is a plan view of the three gyroscopic rings connected to eachother by a series of rotatable joints;

FIG. 24 is a perspective view of the three gyroscopic rings connected toeach other by a series of rotatable joints;

FIG. 25 is another perspective view of the three interconnectedgyroscopic rings connected to each other by a series of rotatablejoints; and

FIG. 26 is a perspective view of the three gyroscopic rings rotated soas to be contained in a single plane.

BEST MODE FOR CARRYING OUT THE INVENTION

1. Overview

The following information provides a basis for understanding of theprinciples underlying the operational elements of the invention,specifically the forces associated with spinning masses of ring geometryand the magnetic basis for brushless motors, including the use of HallEffect sensors. Those skilled in the art may proceed directly to thedetailed description of the invention below.

Forces Associated With Ring Geometry

In assessing the patterns of angular motion that best reveal theinfluence of the cosmic environment the following consideration isapparent. In the formulas defining rotational inertia, the formula foran ideal ring (I=MR²) is mathematically superior for the purpose ofmaximizing the ratio of angular momentum to the mass, more so than forany other single shape. This mathematical relationship is most idealwhen the ring is as thin as possible, when all of the mass is equallyfar from the center of rotation. But the practical application of thisprinciple requires that the ring have some thickness. The formula toaccommodate the thickness factor of a ring is I=M/2(R₁ ²+R₂ ²), where R₁is the inside radius and R₂ is the outside radius. Additionally, theradius is typically constrained by manufacturing limitations and thecost of the materials.

Lorentz Devices

There are several sensors that use the Lorentz force, or Hall Effect, oncharge carriers in a semiconductor. The Lorentz force equation describesthe force F_(L) experienced by a charged particle with charge q movingwith velocity v in a magnetic field B:F _(L) =q(v××B)

Since F_(L), v, and B are vector quantities, they have both magnitudeand direction. The Lorentz force is proportional to the cross productbetween the vectors representing velocity and magnetic field; it istherefore perpendicular to both of them and, for a positively chargedcarrier, has the direction of advance of a right-handed screw rotatedfrom the direction of v toward the direction of B. The accelerationcaused by the Lorentz force is substantially perpendicular to thevelocity of the charged particle; therefore, in the absence of any otherforces, a charge carrier follows a curved path in a magnetic field.

The Hall Effect is a consequence of the Lorentz force in semiconductormaterials. When a voltage is applied from one end of a slab ofsemiconductor material to the other, charge carriers begin to flow. Ifat the same time a magnetic field is applied perpendicular to the slab,the current carriers are deflected to the side by the Lorentz force.Charge builds up along the side until the resulting electrical fieldproduces a force on the charged particle sufficient to counteract theLorentz force. This voltage across the slab perpendicular to the appliedvoltage is called the Hall voltage.

Hall Effect Sensors

Hall Effect sensors typically use n-type silicon when cost is of primaryimportance and GaAs for higher temperature capability due to its largerband gap. In addition, InAs, InSb, and other semiconductor materials aregaining popularity due to their high carrier mobilities that result ingreater sensitivity and frequency response capabilities above the 10-20kHz typical of Si Hall sensors. Compatibility of the Hall sensormaterial with semiconductor substrates is important since Hall sensorsare often used in integrated devices that include other semiconductorstructures.

In most Hall sensors, charge carriers are deflected to the side andbuild up until they create a Hall voltage across the slab with a forceequaling the Lorentz force on the charge carriers. At this point thecharge carriers travel the length in approximately straight lines, andno additional charge builds up. Since the final charge carrier path isessentially along the applied electric field, the end-to-end resistancechanges little with the magnetic field. When the Hall voltage ismeasured between electrodes placed at the middle of each side, theresulting differential voltage is proportional to the magnetic fieldperpendicular to the slab. It also changes sign when the sign of themagnetic field changes. The ratio of the Hall voltage to the inputcurrent is called the Hall resistance, and the ratio of the appliedvoltage to the input current is called the input resistance. The Hallresistance and Hall voltage increase linearly with applied field toseveral teslas (tens of kilogauss). The temperature dependence of thevoltage and the input resistance is governed by the temperaturedependence of the carrier mobility and that of the Hall coefficient.Different materials and different doping levels result in tradeoffsbetween sensitivity and temperature dependence.

2. Detailed Description

To use the principles of rotational energy and momentum as a mechanismof action, a device or machine needs to be created that embodies theapplication of the rotational energy and momentum. Accordingly, thepresent invention uses a brushless electric motor design built to spin amagnetically patterned ring like the rotor of a gyroscope to provide thedesired mechanism for exploitation of the principles of angular energyand angular momentum in a gravitational field. The present inventionemploys three of these motors, positioned at right angles to each otherto achieve stability in a specific frame of reference. The three ringsare housed in a spherical container that is constructed from anon-metallic material.

Ring geometry of individual spinning masses is the basis to allow forthe required association of three of these masses that are equal intheir production of angular momentum and kinetic energy at the sameangular velocities. The result of this association will allow for themechanical control of the net rotational inertia of the revolving massby the control of the individual rotating masses. These individualrotating ring masses are placed at 90-degree angles with respect to oneanother so that each individual ring mass will have force that affectsthe other rotating ring masses identically. The composite revolving masswill exhibit rotational inertia far in excess of the rotational inertiaattributed to the mass when not in this precise motion association. Thismechanically induced force of rotational inertia will manifest itself asa force to oppose the gravitational field surrounding the compositerevolving mass when it reaches the threshold magnitude for thegravitational environment of its then current placement.

The mechanism used for the demonstration of this principle is based on abrushless electrical motor designed to produce large amounts of angularmomentum in proportion to the mass of the motor. Three brushless motorsof ring geometry are used to create the composite motor. Each of thethree brushless motors is designed to produce the same amount of angularmomentum and kinetic energy at the same angular velocity. This isaccomplished by carefully selecting the material used to construct therotor portion of the brushless motors.

These brushless motors are designed to be powerful gyroscopic actuatorsproducing large amounts of stabilizing rotational force. Each individualring rotor is a ring-like mass housed within a containment ring. Thecontainment ring is used to contain and control the mechanical spin ofthe ring rotor and is also the housing for the electrical drive coilsfor the brushless motors. In general, it is desirable that the ringrotor be engineered to be as heavy and massive as possible and that thecontainment ring be as light and of minimal mass as is possible whilestructurally rigid enough to maintain the containment of the movingrotor. The ring rotor rides on the inside surfaces of the containmentring and is supported by a series of bearings and is driven around by aseries of drive coils acting on permanent magnets mounted in the rotor.In the most preferred embodiment of the present invention, a series of 6sets of bearings is driven around by 4 drive coils acting on 6 permanentmagnets mounted in the rotor.

The apparatus is fundamentally an engine that includes three separaterotatable gyroscopic ring rotors, where each of the three gyroscopicring rotors lies in a separate and distinct plane and in at least onepreferred embodiment of the present invention, where each of the threeplanes is perpendicular to the other two planes (X, Y, and Z). Each ofthe gyroscopic ring rotors is capable of achieving substantially thesame angular momentum at substantially the same angular velocity, as iseach of the other two gyroscopic ring rotors. By simultaneously spinningeach of the three gyroscopic ring rotors, the composite superstructurecomprised of the three individual ring rotors resists rotation in anysingle direction. This is known as “equal force presence.” Further, whenthe rate of rotation for the three spinning ring rotors reaches theappropriate level, the composite structure of the three associated ringsresists any change in orientation from any external force, including thegravitational field of the earth or other bodies large enough togenerate a significant gravitational field. Accordingly, as the earthspins about its axis, the mechanism moves in the only directionpossible, which is up, or away from the center of mass for the bodyexerting the gravitational force. By adjusting the angular momentum ofeach of the rings relative to the other rings, or by adjusting therelative angle between the planes of rotation, altitudinal anddirectional changes of the apparatus can be achieved. Each of the threegyroscopic ring rotors housed within the containment ring may be calleda “gyro actuator.”

The stabilizing force exerted by each gyro actuator is positionedagainst the forces exerted by the associated gyro actuators, so that amotion feedback loop is created. This composite superstructure ofangular momentum will exhibit a resistance to any force of torque fromany direction, making for what can be called super-additive rotationalinertia. The rotational inertia of this composite superstructure isrelated to the angular momentums of the individual gyro actuators. Aslong as the forces of the individual rotors are correctly matched andbalanced against one another, an internal force of stabilization orequal force presence can be achieved. With a high enough level ofangular momentum, this internal force will exceed any influence ofexternal force in the surrounding environment; including the rotationaltorque associated with the force of gravity in a given gravitationalfield. Obviously, the greater the gravitational field, the greater thekinetic energy and angular momentum that will be required to overcomethe gravitational forces associated with a given environment.

Since it is desirable to maximize angular momentum with respect to mass,the suspension system housing and containing the ring rotor, and actingas an electric stator magnetically inducing the revolving motion of therotor, is constructed to be as lightweight as possible. The angularacceleration of the ring does not need to be more than the necessaryamount to increase angular velocity and momentum and, eventually, reachthe desired level. This rate of increase can be gradual, and time can begiven for this force to accumulate.

The energy put into the system is converted into the kinetic energy ofrotation, minus any loss of energy as heat due to frictional resistance.The amount of energy that can be stored within the system without largelosses due to the frictional resistance of rotation and precessionalmotion depends at least in part on the perfection of the gyro design andconstruction. If sufficiently perfect, the generation of tremendousamounts of kinetic energy can be accumulated in the form of angularmomentum. The degree of the precision of the perfection of thiscomponent, thereby minimizing frictional resistance, is a factor indetermining its efficiency and effectiveness as a gyro actuator.

If the angular momentum is sufficient, and the containment andsuspension system is sufficiently lightweight and free to move, onlybeing anchored at one point to prevent the backspin of this containmentring, the rotor ring will carry the containment ring with it,duplicating any of its secondary angular displacement. And, like a heavypendulum or a gyro compass, it will maintain its cosmic orientation inspace adjusting to a point of maximum stability until harmony with thespinning earth and the cosmic environment is achieved. The finalorientation of a free and unrestrained spinning ring gyro is with itsaxis of rotation approximately parallel to the earth's axis except thatit will be spinning in the opposite or complementary direction.

The velocity of rotation and the rotational inertia are the factors thatdetermine the magnitude of the force of the angular momentum of the ringrotor and can be calculated, after accounting for factors such asfriction and the inertia of the containment ring as retarding factors ofgenerated force, which will negatively impact the overall performance ofthe system.

The spin of a ring with minimum frictional resistance to rotation, oncestabilized with respect to gravity, if free to move in any direction,will, at a rate proportional to its ratio of angular momentum withrespect to mass, continue to adjust with respect to the environmentuntil the point of maximum stabilization is reached on a continuingbasis. This position of maximum stabilization is oriented so that theaxis of the spinning gyro is approximately parallel to the axis of thespinning earth, yet spinning in the opposite or complementary direction.Thus, the action of a ring gyro actuator with sufficient magnitude ofangular momentum will exhibit a predilection to orient itself into adefinitive position with respect to the cosmic environment in order toattain optimum stabilization with a substantial force.

Ring gyroscopes of differing dimensions can be manufactured such thatthey will be equal in the amount of angular force each will produce atthe same angular velocity. This can be accomplished by carefullyselecting the materials that are used for the rotors of each of thethree brushless motors. The basic force of angular momentum can becalculated for different sizes of rotating ring rotors made fromdifferent materials. By measuring the forces of two different sized ringgyroscopes, including their containment and stator masses, the techniqueof interpolation can be used to create three concentric ring gyroscopesthat are substantially equal in respect to the force of their respectiveangular momentums and kinetic energies. Except for the dimension fromthe center of rotation, these ring-like gyroscopes will havesubstantially identical force attributes.

Given that ring gyroscopes can be made in different sizes, it isdesirable to balance the density of the rotors, so that each of thedifferent sized ring gyroscopes will exhibit, to the extent practical,substantially the same angular momentum while revolving at substantiallythe same angular velocity. Arranging three concentric ring gyroactuators, though different in size, being substantially equal in force,into a composite system in which each of the rings are inclined ninetydegrees with respect to one another and joined into this position by acontainment system creates the fundamental propulsion system of thepresent invention.

With the existence of these individual ring-like gyroscope actuators,the primary component exists from which a concentric ring gyroscopesuperstructure can be built. In one preferred embodiment of the presentinvention, the containment rings in the superstructure, at ninety degreeangles to one another, are locked into place with respect to each other,roughly forming a sphere shaped cage in which the forces of action onthe containment rings are distributed around the periphery of thespherical cage in substantially equal and symmetrical manner withrespect to the effects of the associated revolving forces.

This superstructure is then placed in a final light, hollow, and thin,yet strong sphere. This composite structure will resist torque from anyand all directions equally, so long as the individual forces of eachcomponent ring are equal and balanced with respect to one another. Theincrease in the force of angular momentum of each individual componentincreases the resistance of the superstructure to any outside torque,including the overall frame of gravitational forces associated with theearth and other masses. The composite superstructure of concentric ringgyroscope actuators exhibits the super-additive force of maximumrotational inertia.

Knowing that the composite superstructure will resist torque from anydirection is only one consideration of the result of this compositemotion. The three individual gyroscopes, placed in an orientation suchthat each is offset by ninety degrees to one another in a compositesuperstructure, cannot all be simultaneously in maximum equilibrium withrespect to any cosmic environment that is held by the force of gravity,in an angular revolution, as is the case on the surface of a planet likethe earth. When in such an environment, each of the three individualgyros will continue to exert their individual influences of actiontoward maximum stabilization, but all the while the compositesuperstructure will not be able to absorb any precessional adjustments.Any single gyro actuator, by precessing to adjust to the force of torquewill, of necessity, cause the other two gyro actuators to require thissame adjustment, doubling the problem within the composite system, thuscreating a motion feedback loop that has no resolution within thesystem.

Only by being insulated by sufficient distance from the influence ofgravity in the cosmic environment will the composite superstructure ofinterlocked gyroscopes find equilibrium. The superior resistance totorque will direct this system of motion to the environment, which isthe freest from torque exerted by the gravitational forces inherent in atypical gravitational field. The degree of the magnitude of thiscomposite force of resistance to torque is mechanically connected to,and dependent on, the individual force of each component gyroscope.Gravity is overcome when enough energy is generated by the system thatthe resistance to torque reaches a threshold resulting in a force ofdisplacement in the direction where least external force, manifesting astorque, exists. And this direction is generally away from any and allgravitational sources, including planets and other bodies of masslocated within the universe.

The mass, shape, and speed of rotation are factors in the measurement ofangular momentum, but shape and mass are the only significant factors indetermining rotational inertia. This is true except in the specialcircumstance when the mass is spinning and angular momentum itselfresists any secondary force of torque or tumble against the primaryangle of rotation. Any secondary tumbling force is distributed about theperiphery of the spinning object as precessional motion that will slowthe primary velocity of rotation until a final balance of a single axisof rotation is achieved. This super-additive effect of increasedrotational inertia of the mass in every direction except the one ofprimary rotation underscores the fact that an object rotating resiststumbling; there can be only one axis of rotation.

This composite superstructure of angular momentum will exhibit aresistance to any force of torque from any direction, making for whatcan be called “super-additive rotational inertia.” The rotationalinertia of this composite superstructure is proportional to the angularmomentum of the individual spinning rings. As long as the forces of therotors are balanced against one another, a tremendous internal force ofstabilization is accumulated. This internal force can exceed the angularinfluence of external forces in the immediate surrounding environment.This includes even the force of gravity, which generally requires torqueas an integral component in achieving its result.

Referring now to FIG. 1, the three different planes of initial rotationfor a gyroscopic propulsion device according to a preferred embodimentof the present invention are shown. As shown in FIG. 1, a first plane110 is perpendicular to a second plane 120 and to a third plane 130.Similarly, second plane 120 is perpendicular to third plane 130. Thus,each of the three planes of rotation is perpendicular to the other twoplanes of rotation. For the purposes of the present invention, each ofthe three gyroscopes will provide a ring-like rotating mass in one ofthese planes.

Referring now to FIG. 2, an exploded view of the basic components of agyroscopic ring 200 in accordance with a preferred embodiment of thepresent invention is shown. As shown in FIG. 2, gyroscopic ring 200includes an upper half-shell 210, a rotor element 220, and a lowerhalf-shell 230. Upper half-shell 210 and lower half-shell 230 form acontainer for rotor element 220 and are most preferably constructed froma high-strength, durable, non-metallic, light-weight material such asVespel® made by Dupont®. Upper half-shell 210 and lower half-shell 230are ring-shaped shell elements which are joined together and form acontainment ring or housing for rotor element 220. Rotor element 220 isa spinning ring-shaped mass and is most preferably constructed fromdurable metals such as titanium, stainless steel, etc. The specificmaterials used in manufacturing rotor elements 220 are described ingreater detail in appendix A to this specification. The specific designof the internal surfaces of the upper half-shell 210 and lowerhalf-shell 230 are described in greater detail in FIG. 20.

Rotor 220 is carefully machined such that the inner and outer diameterof rotor 220 is slightly smaller than the inner diameter of upperhalf-shell 210 and lower half-shell 230. Additionally, the overallthickness of rotor 220 is slightly less than the interior space providedwithin the housing formed by upper half-shell 210 and lower half-shell230. This allows rotor 220 to rotate rapidly yet freely within thehousing formed by the union of upper half-shell 210 and lower half-shell230. Since rotor 220 will be rotating or spinning at a high rate, it isdesired that all of the components be durable and of high-qualityworkmanship. Further detail regarding the manufacture of rotor 220,upper half-shell 210, and lower half-shell 230 is described inconjunction with FIG. 5.

Referring now to FIGS. 3 and 4, a representative gyroscopic ring 200 isshown. In order to construct a gyroscopic propulsion device inaccordance with the preferred embodiments of the present invention,three gyroscopic rings 200 will be needed, with each of the three ringshaving the same density. FIG. 3 depicts the general physical nature ofthe various components of a representative rotor element 220 of arepresentative gyroscopic ring 200 and FIG. 4 depicts the exteriorhousing of a representative gyroscopic ring 200 with a series of copperwindings 410. In the preferred embodiments of the present invention,gyroscopic ring 220 serves as the rotor of a brushless motor. Rotorelement 220 includes a series of bearings 320 and a series of magnets350.

As shown in FIG. 3, each set of bearings 320 are spaced equidistantaround the circumference of gyroscopic ring 220. Similarly, magnets 350are also spaced equidistant around the circumference of gyroscopic ring220. In the preferred embodiments of the present invention, there are anequal number of bearings 320 and magnets 350 embedded into the body ofgyroscopic ring 220. In the most preferred embodiment of the presentinvention, the number of bearings 320 is six and the number of magnets350 is also six.

Magnets 350 are embedded into the body of rotor element 220 so as tointeroperate with copper windings 410 and create the drive mechanism forthe brushless motor that propels rotor element 220 within the housing ofgyroscopic ring 200. Magnets 350 are neo-dimium ferrous boron magnets.Magnets 350 are high-grade magnets generating a magnetic force ofapproximately 4,800 gauss each. Magnets 350 are electrically connectedin sets, with each set being connected in parallel.

Bearings 320 are recessed into the body of rotor element 220 and serveto minimize the amount of surface contact area between rotor element 220and the housing of gyroscopic ring 200. In the most preferredembodiments of the present invention, bearings 320 are high-grade gyrobearings manufactured from non-magnetic stainless steel. This allowsrotor element 220 to rotate rapidly with the housing of gyroscopic ring200 with a minimal amount of loss due to friction. Bearings 320 are mostpreferably constructed from high quality stainless steel and to be asresistive to friction as possible.

Although the design of each of the gyroscopic rings 200 used in thegyroscopic propulsion device is similar in nature, the density of thematerial used in the construction of each of the rotor elements 220 foreach of the gyroscopic rings 200 is different. The different densitiesof the materials will allow the overall density of each of the rings tobe equal since the interconnected nature of the rings dictates that eachof the three rings has a different diameter. In at least one preferredembodiment of the present invention, the three rings are associated suchthat each of the three rings is capable of being positioned at 90°relative to the other two rings. In another preferred embodiment of thepresent invention, the three rings are capable of rotating around anaxis and being repositioned relative to the other rings, including oneorientation where all three rings lie in substantially the same plane.

The size and densities of the three rings are designed such that each ofthe three gyroscopic rings achieves the same angular momentum at thesame angular velocity. This careful balancing of gyroscopic rings 200allows the gyroscopic propulsion device to achieve a remarkablestability that resists any outside force of movement. Detailedspecifications for each of the three gyroscopic rings are contained inappendix A to this application.

Referring now to FIG. 4, a plan view depicting the exterior of arepresentative gyroscopic ring 200 according to a preferred embodimentof the present invention is shown. The exterior includes copper windings410 and Hall Effect sensors 420. In the most preferred embodiment of thepresent invention, the number of copper windings 410 is four. Each ofthe four copper windings 410 is a comprised of a series of windings ofcopper wire made around the body of gyroscopic ring 200 at points spaced90° apart. Copper windings 410 cooperate with magnets 350 to provide thepropulsion for rotor element 220 within the housing of gyroscopic ring200 in a manner consistent with typical operation of a brushless motor.Additionally, copper windings 410 serve to hold upper half-shell 210 andlower half-shell 230 together.

In the most preferred embodiments of the present invention, each copperwinding 410 is made using “turns” of approximately 28 gauge copper wire.In the most preferred embodiments of the present invention, each copperwinding 410 is approximately 1.25 inches for each layer of copperwinding 410. Approximately 14 layers of copper are wound around the bodyof gyroscopic ring 200. It is desirable to keep the weight of copperwindings 410 to a minimum yet have enough copper to create thrustsufficient to efficiently spin rotor element 220 within the body createdby upper half-shell 210 and lower half-shell 230.

Copper windings 410 operate in pairs for a single circuit and each of apair of copper windings 410 that are located opposite each other form asingle circuit. Accordingly, there are two circuits for the arrangementshown in FIG. 4. Additionally, each of the pairs of copper windings 410for each of the two circuits operates in conjunction with a single HallEffect sensor 420 to determine the location of magnets 350, therebyallowing the effective operation of the brushless motor.

Hall Effect sensors 420 are used to sense the position of magnets 350 aspart of a feedback loop, which is used to control the rate of angularvelocity for the gyroscopic rings. The use of Hall Effect sensors 420 inthe overall control of the circuit is explained in greater detail inconjunction with FIG. 8. Connected to copper windings 410 and HallEffect sensors 420 are a set of control wires. The control wires providea means for transmitting control signals to and from superstructure 700in order to cause the rotors for each of the ring-like gyroscopes torotate.

Referring now to FIG. 5, a cross-sectional view of the interior of arepresentative gyroscopic ring 200 is shown. The housing of gyroscopicring 200 is comprised of upper half-shell 210 and lower half-shell 230,joined at seam 510. A series of interior step portions 520 serve tocontain the lateral movement of rotor element 220 within the housing ofgyroscopic ring 200 as it rotates about its axis of rotation. Similarly,upper half-shell 210 and lower half-shell 230 cooperate to constrain thevertical movement of rotor element 220 within the housing of gyroscopicring 200 as it rotates about its axis of rotation. Each bearing 320comprises a pair of wheels 530 joined together by an axle 540. Axle 540is inserted through an opening formed in the body of rotor element 220.The diameter of wheels 530 is slightly larger than the thickness ofrotor element 220, thereby preventing rotor element 220 from contactingthe housing of gyroscopic ring 200 as it rotates about its axis ofrotation. When fixed in place, bearings wheels 530 are the only point ofcontact with the housing of gyroscopic ring 200 as rotor element 220rotates about its axis of rotation.

Referring now to FIG. 6, a perspective view of a main superstructure 600for a gyroscopic propulsion device in accordance with a preferredembodiment of the present invention is shown. Superstructure 600 iscomprised of gyroscopic ring 200, gyroscopic ring 610, and gyroscopicring 620. Each of the three gyroscopic rings contains a rotor thatrotates within each of the gyroscopic rings. Each of the threegyroscopic rings is fixed in position so that its axis of rotation forthe spinning mass housed within each of the three gyroscopic rings liesin a plane, which is perpendicular to the plane that defines the axis ofrotation for each of the other two spinning masses housed within theother gyroscopic ring containment shells.

The outer diameter of gyroscopic ring 620 is less than the innerdiameter of gyroscopic ring 200 and the outer diameter of gyroscopicring 200 is less than the inner diameter of gyroscopic ring 610. Thisallows gyroscopic ring 620, gyroscopic ring 200 and gyroscopic ring 610to “nest” inside of each other, creating a cage-like sphere structure.

In order to achieve propulsion, each of gyroscopic rings 620, 200, and610 is energized by the combination of their respective magnets andwindings (not shown) to start the rotor element contained within eachrespective gyroscopic ring spinning. The actual length of time requiredto “spin up” the rings is not as important as the gyroscopic ringsachieving the same angular velocity and the same angular momentum. Inaddition, as long as the masses housed within the gyroscopic rings arespinning at the same angular velocity, each of the gyroscopic rings willalso maintain an equal kinetic energy. This equates to equal “forcepresence.”

In the most preferred embodiment of the present invention, gyroscopicring 610 is constructed from a titanium metal having a density of 4.420g/cc, gyroscopic ring 200 is constructed from stainless steel metalhaving a density of 7.886 g/cc, and gyroscopic ring 620 is constructedfrom tungsten nickel alloy metal having a density of 17.000 g/cc.

Depending on the circumference of the gyroscopic rings, the mass of therespective rotor elements, and the angular velocity of the gyroscopicrings, superstructure 600 will reach a point of internal stabilizationthat will resist all outside forces, including the force of gravity. Atthis point, any increase in the angular velocity of the gyroscopic ringscauses superstructure 600 to resist the rotational torque of the earthand seek an internal equilibrium that cannot be reached in its presentlocation with respect to the gravitational field of the earth, or otherbody of mass large enough to create any type of significantgravitational field. Accordingly, superstructure 600 will need to moveto a new location where the forces of internal stabilization can bemaintained. This will cause superstructure 600 to move away from theearth to a distance where the internal stabilization can be maintained.The distance moved will be related to the angular momentum of thespinning masses.

The greater the angular momentum of the spinning masses, the greater thedistance superstructure 600 will need to move. Similarly, by reducingthe angular velocity of the rings, superstructure 600 will begin to moveback towards the earth because the internal stabilization can bemaintained within a smaller distance.

Similarly, movement in directions other than directly away from theearth can be achieved by varying the angular velocity of one or more ofthe gyroscopic rings to create an imbalance in the angular velocities ofthe gyroscopic rings and/or by changing the orientation of thegyroscopic rings with respect to one another.

Referring now to FIG. 7, a perspective view of a housing 700 forcontaining superstructure 600 in accordance with a preferred embodimentof the present invention is shown. Housing 700 consists of an optionalhandle 705, an upper housing 710 and a lower housing 720. Upper housing710 and lower housing 720 contain superstructure 600 and may be joinedtogether in any suitable fashion by using such techniques asscrew-threaded bodies with a threaded collar that securely joins upperhousing 710 to lower housing 720. Other methods of joining upper housing710 to lower housing 720 may include fabricating the edges of upperhousing 710 and lower housing 720 with interlocking or “snap-fit”connectors or latches. One or more optional handles 705 may be attachedto housing 700 in certain preferred embodiments.

Preferably, housing 700 is constructed of a durable, non-metallicmaterial such as high-strength plastic or some other similar material.Additionally, as shown in FIG. 7, housing 700 may contain optionalapertures 715, which are openings in upper housing 710, and/or lowerhousing 720 that allow heat to escape the interior of housing 700. Giventhat the rotors contained with superstructure 600 may be spinningrapidly, thereby generating heat, it is desirable to provide a way forthe heat generated by the spinning masses to escape the interior ofhousing 700.

Superstructure 600 may be fixed in position within the interior ofhousing 700 by using a series of molded posts, containment ridges, orother means sufficient to contain superstructure 600 in place within theinterior of housing 700. Once placed within housing 700, one or moregyroscopic propulsion device can be attached to other objects and thepropulsion generated by the gyroscopic propulsion device can be used tomove objects from one place to another. This would allow the gyroscopicpropulsion device(s) to be used as a propulsion apparatus or engine fora vehicle in applications such as transporting people and goods fromplace to place.

Referring now to FIG. 8, a block diagram of a control system 800 for agyroscopic propulsion apparatus according to a preferred embodiment ofthe present invention is shown. As shown in FIG. 8, control system 800incorporates a computer 805; an I/O interface 835; an interface 845; abus 895; a drive circuit 870; a control circuit 880; and a Hall Effectsensor circuit 890. As those skilled in the art will appreciate, themethods and apparatus of the present invention apply equally to anycomputer system and combination of circuit components. Specifically, itis envisioned that a hand-held computer or palm-computing device mayperform all or substantially all of the functions described inconjunction with computer 805.

Alternatively, control system 800 may be implemented with a FieldProgrammable Gate Array (FPGA), digital control circuitry, or other typeof circuit mechanism. Regardless of the specific implementation, it isdesirable that there be some mechanism provided whereby the rate ofrotation and angular relationship of the three ring-like gyroscopes canbe controlled. In some applications, control system 800 may be containedwithin housing 700 and the various control signals necessary to controlsuperstructure 600 may be transmitted to and from control system 800from an external source via wireless communication means.

Computer 805 suitably comprises at least one Central Processing Unit(CPU) or processor 810, a main memory 820, a memory controller 830, andan I/O interface 835, all of which are interconnected via a system bus860. Note that various modifications, additions, or deletions may bemade to control system 800 and computer 805 as illustrated in FIG. 8within the scope of the present invention such as the addition of cachememory or other peripheral devices. For example, computer 805 may alsoinclude a monitor or other display device (not shown) connected to thesystem bus 860. Alternatively, it is anticipated that computer 805 maybe a terminal without a CPU that is connected to a network as a networkcomputer (NC). In that case, the responsibilities and functions of CPU810 will be assumed and performed by some other device on the network.FIG. 8 is not an exhaustive illustration of any specific control system,computer system or configuration, but is presented to simply illustratesome of the salient features of one preferred embodiment for controlsystem 800.

Processor 810 performs the computation and control functions of computer805, and may comprise a single integrated circuit, such as amicroprocessor, or may comprise any suitable number of integratedcircuit devices and/or circuit boards working in cooperation toaccomplish the functions of a processor. Processor 810 typicallyexecutes and operates under the control of an operating system 822within main memory 820.

I/O interface 835 allows computer 805 to store and retrieve informationfrom drive circuit 870, control circuit 880, and Hall Effect sensorcircuit 890 via bus 895. It is important to note that while the presentinvention has been (and will continue to be) to include a fullyfunctional computer system, those skilled in the art will appreciatethat the various mechanisms of the present invention are capable ofbeing distributed as a program product in a variety of forms, and thatthe present invention applies equally regardless of the particular typeor location of signal to control the apparatus. I/O interface 835 may bea single bus or multiple computer bus structures. Additionally, I/Ointerface 835 may communicate via serial or parallel presentation of thedata using any type of communication protocol and physical connection,including RS-232, Universal Serial Bus (USB) or any other standardconnection means known or developed by those skilled in the art.

Interface 845 is a connection interface for connecting keyboards,monitors, trackballs and other types of peripheral devices to computer805. Although shown as a single interface, interface 845 may actually bea combination of interface connections, each with a separate connectionto bus 860.

Memory controller 830, through use of a processor (not shown) separatefrom processor 810, is responsible for moving requested information frommain memory 820 and/or through I/O interface 835 to processor 810. Whilememory controller 830 is shown as a separate entity, those skilled inthe art understand that portions of the function provided by memorycontroller 830 may actually reside in the circuitry associated withprocessor 810, main memory 820, and/or I/O interface 835.

Although computer 805 depicted in FIG. 8 contains only a single mainprocessor 810 and a single system bus 860, it should be understood thatthe present invention applies equally to computer systems havingmultiple processors and multiple system buses. Similarly, although thesystem bus 860 of the preferred embodiment is a typical hardwired,multi-drop bus, any connection means that supports bidirectionalcommunication in a computer-related environment could be used, includingwireless communication means.

Main memory 820 suitably contains an operating system 822 and a mastercontrol program 825. The term “memory” as used herein refers to anystorage location in the virtual memory space of computer 805. It shouldbe understood that main memory 820 would not necessarily contain allparts of all mechanisms shown. For example, portions of operating system822 may be loaded into an instruction cache (not shown) for processor810 to execute, while other related files may well be stored on magneticor optical disk storage devices (not shown). In addition, although shownas a single memory structure, it is to be understood that main memory820 may consist of multiple disparate memory locations.

Operating system 822 includes the software, which is used to operate andcontrol computer 805. Operating system 822 is typically executed byprocessor 810. Operating system 822 may be a single program or,alternatively, a collection of multiple programs, which act in concertto perform the functions of any typical operating system, whichfunctions are well known to those skilled in the art.

Master control program 825 is the overall control program for controlsystem 800. Master control program 825 communicates with drive circuit870, control circuit 880 and Hall Effect sensor circuit 890 via bus 860and bus 895. Master control program 825 is capable of interpreting thevarious signals received from I/O interface 835 and translating thesignals in order to operate a gyroscopic propulsion apparatus. Mastercontrol program 825 further incorporates a user interface, which allowsan operator to send instructions via bus 895, thereby controlling theoperation of a gyroscopic propulsion device. The user may interact withmaster control program 825 by use of a video display terminal andkeyboard (not shown), which are connected via interface 845.

Bus 895 is any communication path or medium used to transmit signals andprovide communication between computer 805, drive circuit 870, controlcircuit 880 and Hall Effect sensor circuit 890. This includes standardserial and parallel bus structures, regardless of the physical topologyof the communication path or physical medium used. In at least onepreferred embodiment of the present invention, bus 895 is a wirelesscommunication signal.

Drive circuit 870 contains a power supply 875 which is physicallyconnected to coils 410 and is used to deliver approximately 2-8 amps at90-180 volts to coils 410, thereby causing rotors 220 to rotate withinthe housing of gyroscopic rings 200. Those skilled in the art willunderstand that the operation of drive circuit 870 to control the rateof rotation for rotors 220 is similar to the operation of a standardbrushless motor. Drive circuit 870 delivers the precise amount ofelectricity to coils 410 at precisely the right time.

Control circuit 880 is a timing circuit that is used to calculate thespeed of rotors 220 and communicates with drive circuit 870 to controlthe timing for operating the gyroscopic propulsion apparatus.

Hall Effect sensor circuit 890 relays information from Hall Effectsensors 420 and is used to locate the position of magnets 350 withrespect to coils 410 as rotor 220 rotates. The location of magnets 350is sent to master control program 825 for additional processing. Thisallows master control program 825 to send signals to control circuit 880and control circuit 880 will communicate with drive circuit 870 whichwill energize coils 410 in the appropriate sequence at the appropriatetime to each drive rotor 220, thereby creating the angular momentum ofsuperstructure 600. While the controls are shown as separate circuits,drive circuit 870, control circuit 880, and hall effect sensor circuit890 may be combined into a single circuit and integrated with a computer805 for certain applications.

Referring now to FIG. 9, a perspective view of a vehicle 900incorporating the gyroscopic propulsion apparatus in accordance with apreferred embodiment of the present invention is shown. Vehicle 900 ismerely representative of any type of vehicle known to those skilled inthe art and may take the shape or form thereof. Vehicle 900 willpreferably have one or more gyroscopic propulsion units 910. Mostpreferably, Vehicle 900 will have at least two gyroscopic propulsionunits 910, where each gyroscopic propulsion unit 910 is configured andcontrolled as described in conjunction with FIGS. 1-8.

The present invention provides several different methods for fixing theposition of rings 200, 610, and 620 of FIG. 6 relative to the other. Onesuch preferred embodiment of the present invention, using a series ofinterlocking components to create a support pedestal for rings 200, 610,and 620, is described in conjunction with FIGS. 10-22.

Referring now to FIG. 10, a top view of a z-plane pedestal component1000 in accordance with a preferred embodiment of the present inventioncomprises: one or more optional cooling apertures 1010; assembly slots1020; ring guides 1030; and connection apertures 1040. Z-plane pedestalcomponent 1000 is one component used in conjunction with other similarcomponents to create a support pedestal. Z-plane 1000 is preferablymanufactured from a lightweight rigid material such as heavy-dutyplastics or ceramics. The material should be relatively resistant to theeffects of heat. One such suitable material is Vespel® manufactured byDupont®.

Optional cooling aperture 1010 provides for heat dissipation duringoperation of the preferred embodiments of the present invention.Assembly slots 1020 are provided to allow the various pedestalcomponents to fit together. Ring guides 1030 are cutout portions ofz-plane pedestal component 1000 and are configured to support and secureat least two of the three containment rings housing each of rings 200,610, and 620 in position relative to the other rings. Connectionapertures 1040 are provided to secure two z-plane pedestal components1000 together. A total of four z-plane pedestal components 1000 are usedto assemble a single pedestal.

Referring now to FIG. 11, a top view of a y-plane pedestal component1100 in accordance with a preferred embodiment of the present inventioncomprises: one or more optional cooling apertures 1110; assembly slots1120; ring guides 1130; and connection apertures 1040. Y-plane pedestalcomponent 1100 is one component used in conjunction with other similarcomponents to create a support pedestal. Y-plane pedestal component 1100is preferably manufactured from a lightweight rigid material such asheavy-duty plastics or ceramics. The material should be relativelyresistant to the effects of heat. One such material is Vespel®manufactured by Dupont®.

Optional cooling apertures 1110 provides for heat dissipation duringoperation of the preferred embodiments of the present invention.Assembly slots 1120 are provided to allow the various pedestalcomponents to fit together. Ring guides 1130 are cutout portions ofz-plane pedestal component 1100 and are configured to support and secureat least two of the three containment rings housing each of rings 200,610, and 620 in position relative to the other rings. Connectionapertures 1140 are provided to secure two y-plane pedestal components1100 together. A total of four y-plane pedestal components 1000 are usedto assemble a single pedestal.

Referring now to FIG. 12, a top view of a x-plane pedestal component1200 in accordance with a preferred embodiment of the present inventioncomprises: one or more optional cooling apertures 1210; assembly slots1220; ring guides 1230; and connection apertures 1240. X-plane pedestal1000 is one component used in conjunction with other similar componentsto create a support pedestal. X-plane 1200 is preferably manufacturedfrom a lightweight rigid material such as heavy-duty plastics orceramics. The material should be relatively resistant to the effects ofheat. One such material is Vespel® manufactured by Dupont®.

Optional cooling apertures 1210 provides for heat dissipation duringoperation of the preferred embodiments of the present invention.Assembly slots 1220 are provided to allow the various pedestalcomponents to fit together. Ring guides 1230 are cu-out portions ofx-plane pedestal component 1200 and are configured to support and secureat least two of the three containment rings housing each of rings 200,610, and 620 in position relative to the other rings. Connectionapertures 1240 are provided to secure two x-plane pedestal components1200 together. A total of four x-plane pedestal components 1200 are usedto assemble a single pedestal.

Referring now to FIG. 13, an exploded view of a half pedestal 1300 inaccordance with a preferred embodiment of the present inventioncomprises: two z-plane pedestal components 1000; two y-plane pedestalcomponents 1100; two x-plane pedestal components 1200; and a pair ofconnectors 1310. Assembly slots 1020, 1120, and 1220 are configured toslide into one another, allowing for assembly of half pedestal 1300.Once the pedestal components are assembled, connecters 1310 are insertedinto assembly apertures 1040, thereby securing z-planes 1000 togetherand, in turn, fixing the remaining pedestal components in place.

Referring now to FIG. 14, a perspective view of the assembled halfpedestal 1300 of FIG. 13 is depicted.

Referring now to FIG. 15, an exploded view of two half pedestals 1300 inaccordance with a preferred embodiment of the present invention isdepicted. As shown in FIG. 15, the two half pedestals 1300 are identicalin form and are comprised of the same number and shape of pedestalcomponents.

Referring now to FIG. 16, a perspective view of two assembled pedestalhalves 1300 in accordance with a preferred embodiment of the presentinvention are depicted;

Referring now to FIG. 17, a perspective view of an assembled pedestal1700 in accordance with a preferred embodiment of the present inventionis depicted. As shown in FIG. 17, assembled pedestal 1700 comprises twohalf pedestals 1300.

Referring now to FIG. 18, a perspective view of two pedestal halves 1300supporting gyroscopic rings 200, 610, and 620 in accordance with apreferred embodiment of the present invention is depicted. As shown inFIG. 18, rings 200, 610, and 620 are fixed in position by ring guides1030, 1130, and 1230.

Referring now to FIG. 19, a perspective view of assembled pedestal 1700containing gyroscopic rings 200, 610, and 620 in accordance with apreferred embodiment of the present invention is depicted.

Referring now to FIG. 20, an exploded view of an alternative preferredembodiment of a housing 2000 for assembled pedestal 1700 containinggyroscopic rings 200, 610, and 620 in accordance with a preferredembodiment of the present invention is depicted. As shown in FIG. 20,housing 2000 comprises an upper housing 2010 and a lower housing 2020.

Referring now to FIG. 21, a perspective view of housing 1700 containingthe assembled pedestal 1700 and gyroscopic rings 200, 610, and 620 inaccordance with a preferred embodiment of the present invention;

Referring now to FIG. 22, a perspective view of gyroscopic rings 200,610, and 620 with the rings fixed in position relative to each other inaccordance with an alternative preferred embodiment of the presentinvention is depicted. As shown in FIG. 22, rings 200, 610, and 620 arefixed in position by a series of ring clamps 2210. Each ring clamp 2210secures two rings to each other, preventing the rings from movingrelative to each other.

Referring now to FIG. 23, a plan view of gyroscopic rings 200, 610, and620 is depicted. As shown in FIG. 23, rings 200, 610, and 620 areconnected to each other by a series of rotatable joints 2310. Rotatablejoints 2310 are configured to allow rings 200, 610, and 620 to rotateabout their respective axis, thereby changing the relationship of theplanes in which their ring-like masses rotate. Rotatable joints 2310 areany type of rotating members suitable for allowing the movement of therings relative to each other. One end of each rotatable joint 2310 isfixed to one ring and the other end of each rotatable joint 2310 isaffixed to another ring. By adjusting the relative position of rings200, 610, and 620 relative to each other, the equal force presencegenerated by the angular momentum of rings 200, 610, and 620 can bechanged. This allows for directional control. Master control program 825of FIG. 8 is logically connected to rotatable joints 2310 and isconfigured to control the movement of rotatable joints 2310, therebycontrolling the movement of rings 200, 610, and 620. The logicalconnection to rotatable joints 2310 may be a physical connectioncomprising one or more wires or a wireless connection.

Referring now to FIG. 24, a perspective view of gyroscopic rings 200,610, 620 connected to each other by a series of rotatable joints isdepicted.

Referring now to FIG. 25, another perspective view of gyroscopic rings200, 610, and 620 connected to each other by a series of rotatablejoints is depicted.

Referring now to FIG. 26, a perspective view of gyroscopic rings 200,610, and 620 rotated so as to be contained in a single plane isdepicted.

Yet another exemplary embodiment of a preferred implementation of thepresent invention may be an amusement apparatus capable of resistingrotational movement from an external source, including manipulation by ahuman being. In this embodiment, an optional handle or handles 705, asshown in FIG.7, may be affixed to the exterior surface of housing 700.When the apparatus is energized, the three ring-like gyroscopes are spunup enough to generate a level of angular momentum capable of resistingexternal torque. In this configuration, a human can grasp the housing700 or handles 705 and attempt to rotate housing 700 and feel theresistance of the apparatus. This amusement apparatus will provideentertainment as attempts to manipulate the position of the apparatustake place.

While the present invention has been particularly shown and describedwith reference to preferred exemplary embodiments thereof, it will beunderstood by those skilled in the art that various changes in form anddetails may be made therein without departing from the spirit and scopeof the invention. For example, the exact number of windings used tocreate the brushless motors and the implementation of the controlcircuitry allow for many variations and equivalent embodiments withoutvarying in significance. Similarly, the size of the various gyroscopicrings is limited only by the cost and manufacturing limitationsassociated with increasing the size of the gyroscopic rings and theavailability of suitable material for ensuring that the density of therings creates the desired equal angular momentum for each gyroscopicring at any given angular velocity. Finally, it is anticipated thatadvances in the art of suspended rotors will eventually allow thecreation of a propulsion system where there is no physical contactbetween the rotor and the stator element. In this case, the rotor wouldbe held in place by magnetic fields or other mechanisms.

1. An apparatus comprising: a first ring-like mass rotating in a firstplane, said first ring-like mass comprising a first material, said firstmaterial comprising a first density; a second ring-like mass rotating ina second plane, said second ring-like mass comprising a second material,said second material comprising a second density; a third ring-like massrotating in a third plane, said third ring-like mass comprising a thirdmaterial, said third material comprising a third density, wherein saidfirst density is different from said second density and said thirddensity; and said second density is different from said third density;and a control program, said control program being configured to controlthe planar orientation of at least one of said first ring-like mass andsaid second ring-like mass and said third ring-like mass.
 2. Theapparatus of claim 1 wherein: said first rotating ring-like masscomprises a titanium metal rotating ring-like mass; said second rotatingring-like mass comprises a constructed from a stainless steel rotatingring-like mass; and said third rotating ring-like mass comprises atungsten nickel alloy metal rotating ring-like mass.
 3. The apparatus ofclaim 1 wherein: said first rotating ring-like mass is constructed froma titanium metal having a density of 4.420 g/cc; said second rotatingring-like mass is constructed from a stainless steel metal having adensity of 7.886 g/cc; and said third rotating ring-like mass isconstructed from tungsten nickel alloy metal having a density of 17.000g/cc.
 4. The apparatus of claim 1 further comprising: a firstcontainment ring, said first ring-like mass being contained within saidfirst containment ring; a second containment ring, said second ring-likemass being contained within said second containment ring; a thirdcontainment ring, said third ring-like mass being contained within saidthird containment ring; a first rotatable joint connecting said firstcontainment ring to said second containment ring; and a second rotatablejoint connecting said second containment ring to said third containmentring.
 5. The apparatus of claim 4 wherein said control program isconfigured to actuate at least one of said first and second rotatablejoints, thereby altering the planar orientation of at least one of saidfirst containment ring said second containment ring and said thirdcontainment ring
 6. The apparatus of claim 4 further comprising ahousing, said housing containing said containment rings, said rotatablejoints and said ring-like masses.
 7. The apparatus of claim 1 wherein:said first ring-like mass generates a first angular momentum; saidsecond ring-like mass generates a second angular momentum; said thirdring-like mass generates a third angular momentum; and said first,second, and third angular momentums are equal.
 8. The apparatus of claim7 wherein: said first plane is substantially perpendicular to saidsecond plane and said third plane; said second plane is substantiallyperpendicular to said third plane; and said first, second, and thirdangular momentums are equal.
 9. The apparatus of claim 7 wherein: saidfirst plane is substantially non-perpendicular to at least one of saidsecond plane or said third plane; said second plane is substantiallynon-perpendicular to at least one of said first plane or said thirdplane; and said first angular momentum is unequal to at least one ofsaid second and third angular momentums.
 10. A method comprising thesteps of: rotating a first ring-like mass rotating in a first plane,said first ring-like mass comprising a first material, said firstmaterial comprising a first density, said first ring-like massgenerating a first angular momentum; rotating a second ring-like massrotating in a second plane, said second ring-like mass comprising asecond material, said second material comprising a second density, saidsecond ring-like mass generating a second angular momentum; rotating athird ring-like mass rotating in a third plane, said third ring-likemass comprising a third material, said third material comprising a thirddensity, said third ring-like mass generating a third angular momentum;and wherein said first density is different from said second density andsaid third density; and said second density is different from said thirddensity and said first angular momentum is not equal to at least one ofsaid second and third angular momentums.
 11. The method of claim 10wherein: said first plane is substantially perpendicular to said secondplane and said third plane; said second plane is substantiallyperpendicular to said third plane; and said first, second, and thirdangular momentums are substantially equal.
 12. The method of claim 10wherein: said first plane is substantially non-perpendicular to saidsecond plane and said third plane; said second plane is substantiallynon-perpendicular to said third plane; and said first, second, and thirdangular momentums are unequal.
 13. The method of claim 10 furthercomprising the step of varying said first, second, and third angularmomentums by activating a control program.
 14. An apparatus comprising:a first ring-like mass rotating in a first plane, said first ring-likemass comprising a first material, said first material comprising a firstdensity; a second ring-like mass rotating in a second plane, said secondring-like mass comprising a second material, said second materialcomprising a second density; a third ring-like mass rotating in a thirdplane, said third ring-like mass comprising a third material, said thirdmaterial comprising a third density, wherein said first density isdifferent from said second density and said third density; and saidsecond density is different from said third density; a first containmentring, said first ring-like mass being contained within said firstcontainment ring; a second containment ring, said second ring-like massbeing contained within said second containment ring; a third containmentring, said third ring-like mass being contained within said thirdcontainment ring; a control program, said control program beingconfigured to control the rotation of said first ring-like mass and saidsecond ring-like mass and said third ring-like mass, and said controlprogram being configured to control the planar orientation of said firstring-like mass and said second ring-like mass and said third ring-likemass.
 15. The apparatus of claim 14 further comprising: a firstrotatable joint connecting said first containment ring to said secondcontainment ring; and a second rotatable joint connecting said secondcontainment ring to said third containment ring.
 16. The apparatus ofclaim 14 further comprising a housing, said housing containing saidapparatus.
 17. The apparatus of claim 16 further comprising a vehicle,said vehicle containing said apparatus.